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EP3798134B1 - Liaison(s) entre des portes de capot internes et externes - Google Patents

Liaison(s) entre des portes de capot internes et externes Download PDF

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Publication number
EP3798134B1
EP3798134B1 EP20199457.1A EP20199457A EP3798134B1 EP 3798134 B1 EP3798134 B1 EP 3798134B1 EP 20199457 A EP20199457 A EP 20199457A EP 3798134 B1 EP3798134 B1 EP 3798134B1
Authority
EP
European Patent Office
Prior art keywords
cowl door
door
linkage
inner cowl
outer cowl
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP20199457.1A
Other languages
German (de)
English (en)
Other versions
EP3798134A1 (fr
Inventor
Sean PRETTY
Erik Linde
Martin C. BELL
Jihad Ramlaoui
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rohr Inc
Original Assignee
Rohr Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rohr Inc filed Critical Rohr Inc
Publication of EP3798134A1 publication Critical patent/EP3798134A1/fr
Application granted granted Critical
Publication of EP3798134B1 publication Critical patent/EP3798134B1/fr
Active legal-status Critical Current
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/57—Kinematic linkage, i.e. transmission of position using servos, independent actuators, etc.

Definitions

  • This disclosure relates generally to an aircraft propulsion system and, more particularly, to operatively linking components of a nacelle together.
  • a modern aircraft propulsion system includes a nacelle for housing a gas turbine engine.
  • the nacelle may include various cowl doors, which doors are pivotally mounted to provide access to the gas turbine engine and/or accessories configured with the gas turbine engine. While known nacelles and cowl doors have various advantages, there is still room in the art for improvement.
  • a prior art assembly for an aircraft propulsion system having the features of the preamble of claim 1 is disclosed in GB 2 483 908 A . Further prior art assemblies for aircraft propulsion systems are disclosed in US 9 885 253 B2 , WO 2019/129961 A1 , US 2004/068978 A1 and EP 3 103 995 A2 .
  • an assembly is provided for an aircraft propulsion system, as claimed in claim 1.
  • the inner cowl door may have a midpoint halfway circumferentially along the inner cowl door between the first end and the second end.
  • the linkage may be movably connected to the inner cowl door at a connection point circumferentially between the midpoint and the first end.
  • connection point may be circumferentially closer to the first end than the midpoint.
  • the outer cowl door may extend circumferentially between a first end and a second end with a midpoint halfway circumferentially along the outer cowl door between the first end and the second end.
  • the outer cowl door may be pivotally connected to the fixed structure at the first end.
  • the linkage may be movably connected to the outer cowl door at a connection point circumferentially between the midpoint and the first end.
  • connection point may be circumferentially closer to the first end than the midpoint.
  • the linkage may be configured to push against and thereby open the outer cowl door as the inner cowl door is opened.
  • the assembly may also include a lock configured to lock a position of the linkage.
  • the assembly may also include an actuator configured to push open the inner cowl door.
  • the assembly may also include an actuator configured to pull open the outer cowl door.
  • a portion of a bypass flowpath within the aircraft propulsion system may be formed by and may extend radially between the inner cowl door and the outer cowl door.
  • the assembly may also include a nacelle outer structure and a nacelle inner structure.
  • the nacelle outer structure may be configured as or otherwise include the outer cowl door.
  • the nacelle inner structure may be configured as or otherwise include the inner cowl door.
  • the present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof.
  • FIG. 1 illustrates an aircraft propulsion system 10 for an aircraft such as, but not limited to, a commercial airliner or a cargo plane.
  • the propulsion system 10 includes a nacelle 12 and a gas turbine engine.
  • This gas turbine engine may be configured as a high-bypass turbofan engine. Alternatively, the gas turbine engine may be configured as any other type of gas turbine engine capable of propelling the aircraft during flight.
  • the nacelle 12 is configured to house and provide an aerodynamic cover for the gas turbine engine.
  • the nacelle 12 of FIG. 1 includes a nacelle outer structure 14 and a nacelle inner structure 16, which inner structure 16 may sometimes be referred to as an inner fixed structure (IPS).
  • IPS inner fixed structure
  • the inner structure 16 covers a core 18 of the gas turbine engine.
  • This engine core 18 may include a compressor section, a combustor section and a turbine section.
  • the inner structure 16 includes an inner barrel 20 and at least one bifurcation structure 22; e.g., an upper bifurcation cowl.
  • the inner barrel 20 may be a generally cylindrical and/or barrel-shaped cowl that extends circumferentially around and axially along the engine core 18 and/or an axial centerline 23 of the aircraft propulsion system 10 and/or its gas turbine engine, which axial centerline 23 may be coaxial with a rotational axis of the gas turbine engine.
  • the inner barrel 20 at least partially forms an internal compartment 24 (e.g., a core compartment) within the nacelle 12. This internal compartment 24 at least partially or completely houses the engine core 18.
  • the engine core 18 is thereby arranged within the internal compartment 24.
  • the bifurcation structure 22 provides an aerodynamic housing for a pylon 26 which mounts the aircraft propulsion system 10 to the aircraft.
  • the bifurcation structure 22 extends radially between the inner barrel 20 and the outer structure 14.
  • the bifurcation structure 22 and/or the pylon 26 may each be configured as part of a fixed structure 27 of the aircraft propulsion system 10.
  • the outer structure 14 covers a fan section (not shown) of the gas turbine engine; e.g., the outer structure 14 covers a fan case 29 of the fan section; see FIG. 1 .
  • the outer structure 14 covers at least a forward portion of the inner structure 16 and its inner barrel 20 so as to form a bypass duct and an associated bypass flowpath 28 radially between the structures 14 and 16.
  • the outer structure 14 may also be configured with a thrust reverser for redirecting airflow from the bypass flowpath 28 out of the nacelle 12 in a forward and outward direction.
  • the present disclosure is not limited to the foregoing exemplary general nacelle configuration.
  • the bypass duct of FIG. 2 is configured as an O-Duct.
  • the term "O-duct” may describe a duct through which only a single bifurcation extends between and connects a nacelle outer structure and a nacelle inner structure.
  • the term “C-Duct” or “D-duct” may describe a duct through which two bifurcations (e.g., an upper bifurcation and a lower bifurcation) extends between and connect a nacelle outer structure and a nacelle inner structure.
  • the exemplary duct shown in FIG. 2 is an O-duct, the present disclosure is not limited to any particular duct configurations. In particular, the present disclosure also contemplates the nacelle 12 having a C-duct or a D-duct.
  • the inner structure 16 is configured with one or more movable (e.g., pivotable) inner structure components 30.
  • These inner structure components 30 are configured as or otherwise include inner cowl doors 32.
  • Each of these inner cowl doors 32 extends circumferentially about the axial centerline 23.
  • each inner cowl door 32 extends circumferentially between an inner cowl first (e.g., upper) end 34 and an inner cowl second (e.g., lower) end 36.
  • the inner cowl door 32 is pivotally connected to the fixed structure 27 (e.g., the bifurcation structure 22 and/or the pylon 26), such as at the inner cowl first end 34 by, for example, a hinge at a pivot point 37.
  • Each inner cowl door 32 is thereby operable to move (e.g., pivot about the pivot point 37) between an inner cowl door closed position (position of FIG. 2 ) and an inner cowl door open position (position of FIG. 3 ).
  • the inner cowl second ends 36 of the inner cowl doors 32 may be configured to latch together so as to at least partially or completely form the inner barrel 20.
  • the outer structure 14 is configured with one or more movable (e.g., pivotable) outer structure components 38.
  • These outer structure components 38 are configured as or otherwise include outer cowl doors 40.
  • Each of these outer cowl doors 40 extends circumferentially about the axial centerline 23.
  • each outer cowl door 40 extends circumferentially between an outer cowl first (e.g., upper) end 42 and an outer cowl second (e.g., lower) end 44.
  • the outer cowl door 40 is pivotally connected to the fixed structure 27 (e.g., the bifurcation structure 22 and/or the pylon 26), such as at the outer cowl first end 42 by, for example, a hinge at a pivot point 45.
  • Each outer cowl door 40 is thereby operable to move (e.g., pivot about the pivot point 45) between an outer cowl door closed position (position of FIG. 2 ) and an outer cowl door open position (position of FIG. 3 ).
  • the outer cowl second ends 44 of the outer cowl doors 40 may be configured to latch together so as to at least partially or completely form, for example, a translatable sleeve of the outer structure 14.
  • the nacelle 12 is configured with one or more linkages 46.
  • Each of these linkages 46 is connected to a respective one of the outer structure components 38 (outer cowl doors 40) and a respective one of the inner structure components 30 (inner cowl doors 32).
  • each linkage 46 of FIGS. 4 and 5 is moveably (pivotally) connected to the respective outer cowl door 40, for example at a first connection point 49 (e.g., an outer pivot point) via a first pivot joint; e.g., an outer pin connection.
  • a second (e.g., inner) end 50 of each linkage 46 of FIGS. 4 and 5 is moveably (pivotally) connected to the respective outer cowl door 40, for example at a second connection point 51 (e.g., an inner pivot point) via a second pivot joint; e.g., an inner pin connection.
  • Each linkage 46 extends (e.g., radially) between the respective outer cowl door 40 and the respective inner cowl door 32. In the specific embodiment of FIGS. 4 and 5 , each linkage 46 completes a four-bar mechanism between the components 27, 30/32 and 38/40.
  • Each linkage 46 is arranged proximate the fixed structure 27; e.g., the bifurcation structure 22 and/or the pylon 26. Each linkage 46, for example, may be arranged closer to the fixed structure 27 than the ends 36 and/or 44.
  • the first connection point 49 is located circumferentially along the component 38, 40 between the end 42 and a circumferential midpoint 53 (e.g., center) of the component 38, 40, which midpoint 53 may be located circumferentially (e.g., halfway) along the component 38, 40 between its ends 42 and 44.
  • the connection point 49 of FIGS. 4 and 5 for example, is located circumferentially closer to the end 42 than the midpoint 53.
  • connection point 51 is located circumferentially along the component 30, 32 between the end 34 and a circumferential midpoint 55 (e.g., center) of the component 30, 32, which midpoint 55 may be located circumferentially (e.g., halfway) along the component 30, 32 between its ends 34 and 36.
  • the connection point 51 of FIGS. 4 and 5 is located circumferentially closer to the end 34 than the midpoint 55.
  • the present disclosure is not limited to such an exemplary linkage 46 location.
  • the linkages 46 may be located circumferentially towards the midpoints 53, 55.
  • Each linkage 46 is configured to link movement (e.g., pivoting) of the respective outer structure component 38 (e.g., outer cowl door 40) and the respective inner structure component 30 (e.g., inner cowl door 32).
  • the linkages 46 will pull the inner cowl doors 32 open (e.g., concurrently) with the outer cowl doors 40.
  • one or each linkage 46 may be configured as a single rigid link such as, but not limited to, a push (or pull) rod.
  • Each linkage 46 has a longitudinal fixed length.
  • each linkage 46 may be configured with a lock 56; e.g., a locking mechanism.
  • each linkage 46 of FIG. 8 may include two (e.g., fixed or variable length) links 58 and 60 configured to provide an over-center lock when those links 58 and 60 are over extended. With such a configuration, outside the wording of the claims, each linkage 46 may have a longitudinal variable length.
  • one or each linkage 46 may be permanently mounted with the cowl doors 32, 40. In other words, the linkages 46 may remain mounted with the cowl doors 32, 40 during turbine engine operation. However, in other embodiments, one or each linkage 46 may be removably mounted with the cowl doors 32, 40 such that those linkages 46 are removed for turbine engine operation. Thus, the linkages 46 may be installed only for turbine engine maintenance and/or inspection.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)

Claims (12)

  1. Ensemble pour un système de propulsion d'aéronef (10), comprenant :
    une structure fixe (27) ;
    une porte de capot interne (32) s'étendant circonférentiellement entre une première extrémité (34) de porte de capot interne et une seconde extrémité (36) de porte de capot interne, la porte de capot interne (32) étant connectée de manière pivotante à la structure fixe (27) au niveau de la première extrémité (34) de porte de capot interne ;
    une porte de capot externe (40) connectée de manière pivotante à la structure fixe (27), la porte de capot externe (40) étant radialement à l'extérieur et chevauchant la porte de capot interne (32) ; et
    une liaison (46) s'étendant entre et connectée de manière mobile à la porte de capot interne (32) et à la porte de capot externe (40), la liaison (46) étant connectée de manière pivotante à la porte de capot interne (32) et connectée de manière pivotante à la porte de capot externe (40), dans lequel la liaison (46) est agencée à proximité de la structure fixe (27),
    caractérisé en ce que :
    la liaison (46) a une longueur fixe et est agencée plus près de la structure fixe (27) que de la seconde extrémité (36) de porte de capot interne, et la liaison (46) est configurée pour tirer contre et ainsi ouvrir la porte de capot interne (32) lorsque la porte de capot externe (40) est ouverte.
  2. Ensemble selon la revendication 1, dans lequel
    la porte de capot interne (32) a un point médian de porte de capot interne (55) à mi-chemin circonférentiellement le long de la porte de capot interne (32) entre la première extrémité (34) de porte de capot interne et la seconde extrémité (36) de porte de capot interne ; et
    la liaison (46) est connectée de manière mobile à la porte de capot interne (32) au niveau d'un point de connexion de porte de capot interne (51) circonférentiellement entre le point médian de porte de capot interne (55) et la première extrémité (34) de porte de capot interne.
  3. Ensemble selon la revendication 2, dans lequel le point de connexion de porte de capot interne (51) est circonférentiellement plus proche de la première extrémité (34) de porte de capot interne que du point médian de porte de capot interne (55).
  4. Ensemble selon la revendication 1, 2 ou 3, dans lequel
    la porte de capot externe (40) s'étend circonférentiellement entre une première extrémité (42) de porte de capot externe et une seconde extrémité (44) de porte de capot externe avec un point médian de porte de capot externe (53) à mi-chemin circonférentiellement le long de la porte de capot externe (40) entre la première extrémité (42) de porte de capot externe et la seconde extrémité (44) de porte de capot externe ;
    la porte de capot externe (40) est connectée de manière pivotante à la structure fixe (27) au niveau de la première extrémité (42) de porte de capot externe ; et
    la liaison (46) est connectée de manière mobile à la porte de capot externe (40) au niveau d'un point de connexion de porte de capot externe (49) circonférentiellement entre le point médian de porte de capot externe (53) et la première extrémité (42) de porte de capot externe.
  5. Ensemble selon la revendication 4, dans lequel le point de connexion de porte de capot externe (49) est circonférentiellement plus proche de la première extrémité (42) de porte de capot externe que du point médian de porte de capot externe (53).
  6. Ensemble selon une quelconque revendication précédente, dans lequel la liaison (46) est configurée pour pousser contre et ainsi ouvrir la porte de capot externe (40) lorsque la porte de capot interne (32) est ouverte.
  7. Ensemble selon une quelconque revendication précédente, comprenant en outre un verrou (56) configuré pour verrouiller une position de la liaison (46).
  8. Ensemble selon une quelconque revendication précédente, comprenant en outre un actionneur de porte de capot interne (54) configuré pour pousser et ouvrir la porte de capot interne (32).
  9. Ensemble selon une quelconque revendication précédente, comprenant en outre un actionneur de porte de capot externe (52) configuré pour ouvrir la porte de capot externe (40).
  10. Ensemble selon une quelconque revendication précédente, dans lequel une partie d'un trajet d'écoulement de dérivation à l'intérieur du système de propulsion d'aéronef (10) est agencée radialement entre la porte de capot interne (32) et la porte de capot externe (40).
  11. Ensemble selon une quelconque revendication précédente, comprenant en outre :
    une structure externe de nacelle (14) comprenant la porte de capot externe (40) ; et
    une structure interne de nacelle (16) comprenant la porte de capot interne (32).
  12. Ensemble selon la revendication 1, comprenant en outre :
    une structure interne de nacelle (16) comprenant la porte de capot interne (32), la porte de capot interne (32) étant connectée de manière pivotante à la structure fixe (27) au niveau d'un premier point de pivotement (37), et la porte de capot interne (32) étant configurée pivoter autour du premier point de pivotement (37) entre une position fermée de porte de capot interne et une position ouverte de porte de capot interne ; et
    une structure externe de nacelle (14) s'étendant circonférentiellement autour de et chevauchant la structure interne de nacelle (16), la structure externe de nacelle (14) comprenant la porte de capot externe (40), la porte de capot externe (40) étant connectée de manière pivotante à la structure fixe (27) au niveau d'un second point de pivotement (45), et la porte de capot externe (40) étant configurée pour pivoter autour du second point de pivotement (45) entre une position fermée de porte de capot externe et une position ouverte de porte de capot externe,
    la liaison (46) s'étendant entre et étant connectée de manière pivotante à la porte de capot interne (32) au niveau d'un point de connexion de porte de capot interne (51) et à la porte de capot externe (40) au niveau d'un point de connexion externe (49), dans lequel le point de connexion de porte de capot interne (51) est situé circonférentiellement le long de la porte de capot interne (32) entre un point médian de porte de capot interne (55) de la porte de capot interne (32) et le premier point de pivotement (37), et/ou le point de connexion externe (49) est situé circonférentiellement le long de la porte de capot externe (40) entre un point médian de porte de capot externe (53) de la porte de capot externe (40) et le second point de pivotement (45).
EP20199457.1A 2019-09-30 2020-09-30 Liaison(s) entre des portes de capot internes et externes Active EP3798134B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US201962907813P 2019-09-30 2019-09-30

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EP3798134A1 EP3798134A1 (fr) 2021-03-31
EP3798134B1 true EP3798134B1 (fr) 2024-05-29

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11427341B2 (en) * 2019-09-30 2022-08-30 Rohr, Inc. Linkage supporting a door of an aircraft propulsion system

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US4385423A (en) 1980-12-22 1983-05-31 The Boeing Company Over-center latching coupling
FR2560854B1 (fr) * 1984-03-07 1986-09-12 Snecma Capotages structuraux participant a la rigidite d'ensemble d'un turboreacteur
US4679750A (en) * 1984-06-20 1987-07-14 The Boeing Company Latch system
US4585189A (en) * 1984-10-22 1986-04-29 Lockheed Corporation Counterbalanced cowling assembly for a pylon-mounted engine and nacelle therefor
BR0315201A (pt) 2002-10-11 2005-08-16 Nordam Group Inc Inversor de impulsão de dobra dupla
CA2812580C (fr) * 2010-09-24 2018-10-23 Short Brothers Plc Nacelle dotee de portes de capot articulees permettant d'acceder au moteur
GB2483908B (en) * 2010-09-24 2012-07-11 Short Brothers Plc Nacelle
EP2906808A4 (fr) 2012-10-10 2015-11-11 United Technologies Corp Moteur de turbine à engrenages ayant un conduit d et un inverseur de poussée
US9435293B2 (en) 2013-02-22 2016-09-06 United Technologies Corporation Full ring sliding nacelle with thrust reverser
US9221545B2 (en) * 2013-04-03 2015-12-29 The Boeing Company Aircraft nacelle assemblies
CN105765204B (zh) * 2013-10-07 2019-07-30 罗尔公司 具有金属和复合构造的混合式内部固定结构
FR3037039B1 (fr) * 2015-06-03 2017-06-02 Aircelle Sa Dispositif de verrouillage de capots pivotants d’un inverseur de poussee
US10041443B2 (en) 2015-06-09 2018-08-07 The Boeing Company Thrust reverser apparatus and method
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FR3076323B1 (fr) * 2017-12-28 2020-01-10 Safran Nacelles Inverseur de poussee a grilles pour turboreacteur
FR3078111B1 (fr) * 2018-02-22 2020-01-17 Airbus Sas Turboreacteur comportant une nacelle equipee d'un systeme inverseur comportant des portes exterieures et interieures

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US11511874B2 (en) 2022-11-29
US20210094697A1 (en) 2021-04-01
EP3798134A1 (fr) 2021-03-31

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